CN1354322A - Jet rotary engine - Google Patents
Jet rotary engine Download PDFInfo
- Publication number
- CN1354322A CN1354322A CN 00132754 CN00132754A CN1354322A CN 1354322 A CN1354322 A CN 1354322A CN 00132754 CN00132754 CN 00132754 CN 00132754 A CN00132754 A CN 00132754A CN 1354322 A CN1354322 A CN 1354322A
- Authority
- CN
- China
- Prior art keywords
- rotor
- air
- combustion gas
- rotary engine
- fuel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The present invention provides a jet rotary engine. Its core structure is a jet rotor. The air-compressor device, combustion chamber and jet pipe are placed on the jet rotor. Its working principle lines in that when the jet rotary engine is worked, the tangential airstream jetted from jet pipe of rotor can drive rotor and make it rotate to apply work so as to be able to convert the heat energy into machine energy.
Description
The present invention relates to a kind of jet rotary engine, belong to energetics, particularly engine art.
Existing motor can divide three major types according to its hot merit conversion equipment difference: piston type, turbo type, jet-propelled.The basic principle of reciprocating engine is that high-temperature gas expands in piston, and promotes the piston work done, thereby heat energy is converted into mechanical energy.Its typical type is diesel engine and petrol engine, is referred to as internal-combustion engine.The history in existing more than 100 year of the appearance of internal-combustion engine, its production technology is very ripe, and be widely used in various power field, that internal-combustion engine has that efficient is higher, running is reliable, starting is shut down is convenient, acceleration-deceleration rapidly, power and the wide advantage of rotational speed regulation operating range; Up to now, it remains the irreplaceable power of automobile.Its shortcoming is that pollution is high, noise is big, power-weight ratio is less.How to develop the little and function admirable of a kind of pollution, the new work engine that adapts to automobile replaces former internal-combustion engine, is one of current technology most pressing problem.The basic principle of turbo type engine is the high-temperature gas acceleration of expanding in flow channel, and high velocity air promotes turbine rotation work done, thereby heat energy is converted into mechanical energy.Typical case's representative of turbogenerator is steam turbine and gas turbine, and steam turbine is mainly used in power generating equipment and large-sized power, and gas turbine is mainly used in generating, large ship power and aviation field.Gas turbine is one of classic motor, and it has the advantage that running is steady, exhaust emission is minimum, efficient is high, and its deficiency is that speed and power are difficult to regulate, and small-power type difficulty is bigger, is difficult to use in motor car engine.The basic principle of air breathing engine is the high-temperature gas acceleration of expanding in jet pipe, and with ejection at a high speed, high velocity air produces reaction force to jet pipe and promotes the aircraft work done simultaneously, thereby heat energy is converted into mechanical energy.Air breathing engine is divided into the air breathing jet engine and two kinds in the rocket motor that is used for space industry that is used for aviation field.The advantage of air breathing engine is that power-weight ratio is big, simple and reliable for structure, efficient is high, is especially suitable for use as high-speed aircraft power, and its deficiency is to be used for fixing machine power or slow-moving vehicle power.
The present invention provides a kind of jet rotary engine, and its core texture is an air injection rotor (2) of establishing blast tube and fuel gallery in one.Its working principle is the tangential gas flow promotion rotor rotation work done by the injection pipe of blast tube (14) ejection, thereby heat energy is changed into mechanical energy.This jet rotary engine had both had the advantage that air breathing engine is simple in structure, power-weight ratio is big, had the advantage that the turbogenerator running is steady, exhaust emission is little, efficient is high again, and Miniaturizable.
Jet rotary engine is made of body (1), air injection rotor (2), Fuel System (3), combustion gas system (4), starting system (5), power output device (6) six parts.
The function of jet rotary engine body (1) is to provide the mounting point to each parts, and each parts is linked to be an integral body.
The profile of air injection rotor (2) and mass distribution be with respect to the strict symmetry of rotating shaft, and have enough big structural strength, rotor by rotating shaft, Bearing Installation on body (1); Be provided with two or more rotor gas circuit (7) that is distributed symmetrically each other and rotor oil circuit (8) at internal rotor; Every rotor gas circuit (7) is made of suction port (11), the centrifugal air pressure draw (12), firing chamber (13), injection pipe (14) four parts; Suction port (11) is near the rotor end-face axle center, the centrifugal air pressure draw (12) is communicated with suction port (11) and firing chamber (13), firing chamber (13) is in the rotor outside, the distance in axle center is arrived in firing chamber (13) greater than suction port (11) to the distance in axle center, the inlet of injection pipe (14) is in the firing chamber (13), outlet is at rotor side surface, and the centerline average of injection pipe (14) is parallel with the rotor tangent line, also can one little angle be arranged the sub-tangent line of transfer; The inwall of firing chamber (13) and injection pipe (14) is lined with heat insulation temperature-resistant material; Rotor oil circuit (8) is made of oil inlet hole (15), centrifugal fuel pressurization pipe (16), oil injecting nozzle (17) three parts; Oil inlet hole (15) is connected with fuel supply line in rotor axis and by rotary seal, and centrifugal fuel pressurization pipe (16) is communicated with oil inlet hole (15) and oil injecting nozzle (17), and the opening of oil injecting nozzle (17) is in the firing chamber (13); Above scheme is suitable for adopting the jet rotary engine of liquid fuel; According to fuel used difference, air injection rotor (2) also has other two kinds of schemes: a kind of is the gaseous fuel formula, its structural feature is not have rotor oil circuit (8), and gaseous fuel is elder generation and air mixing before entering rotor, enters rotor gas circuit (7) by suction port (11) again; Also having a kind of is the rocket fuel formula, is characterized in carrying liquid fuel and liquid oxidizer, does not need air to get final product work, thereby air injection rotor (2) does not have the suction port (11) and the centrifugal air pressure draw (12).The service performance of rocket fuel formula jet rotary engine is that the working pressure transfer speed of firing chamber (13) is irrelevant, but jet rotary engine need not add the starting arrangement self-drive.
Fuel System (3) is made of fuel tank (21), delivery rate controller (22), fuel supply line (23), several parts of rotor oil circuit (8), and delivery rate controller (22) can provide suitable delivery rate according to instruction of being sent and engine operating condition.
The most complete composition proposal of combustion gas system (4) is made of filter cleaner (31), suction tude (32), prime air compression plant (33), rotor gas circuit (7), back level combustion gas energy conversion device (34), outlet pipe (35); Wherein having only rotor gas circuit (7) is combustion gas system (4) indispensable core; The simplest combustion gas is that (4) organization plan only has rotor gas circuit (7) to constitute; Another scheme is that combustion gas system (4) is provided with prime air compression plant (33), but level combustion gas energy conversion device (34) not; The structure of prime air compression plant (33) is a centrifugal compressor or axial flow compressor, and it can be driven by air injection rotor (2), also can be driven by back level combustion gas energy conversion device (34); A back level combustion gas energy conversion device (34) can be a turbine mechanism, also can be a piston mechanism, and its function is to be the combustion gas Conversion of energy of high-voltage high-speed mechanical work.Flow parameter coupled modes between back level combustion gas energy conversion device (34) and the air injection rotor (2) can employing speed be coupled, the gas pressure that is air injection rotor (2) ejection equals barometric pressure substantially, the combustion gas energy exists with the kinetic energy form basically, and the effect of back level energy conversion device (34) is that the kinetic energy of combustion gas is converted into the rotation merit; Also can adopt coupling pressure, i.e. the gas velocity of rotor (2) ejection is zero substantially, and pressure is greater than barometric pressure, and the effect of back level combustion gas energy conversion device (34) is that the pressure potential of combustion gas is converted into the rotation merit.
Starting system (5) is made of starter motor (41), starting circuit (42), igniter (43); The effect of starter motor (41) is to drive air injection rotor (2) to rotate when jet rotary engine starts, and makes air injection rotor (2) obtain the necessary initial velocity of starting; Igniter (43) is contained in the firing chamber (13), and the acting in conjunction of starting circuit (42) and igniter (43) is when jet rotary engine starts, and carries out initial ignition for firing chamber (13); When running well after the jet rotary engine starting, starting system (5) quits work.
The scheme of power output device (6) has four kinds: the one, directly export by the rotating shaft of air injection rotor (2), promptly by the rotating shaft of air injection rotor (2) directly or by the gear drive load, be the prevailing way of output; The 2nd, by back level combustion gas energy conversion device (34) output, the characteristics of this scheme are that air injection rotor (2) is only as gasifier section work, the high-pressure gas that it produced is converted into mechanical energy in back level combustion gas energy conversion device (34), and drives the load work done; The 3rd, export in the mode of propeller cavitation, the structural feature of this scheme is that itself just to make profile be propeller-like to air injection rotor (2), firing chamber (13) and injection pipe (14) just are located at the outer end of blade, and injection pipe (14) directly promotes the propeller cavitation rotation during jet rotary engine work; The 4th, end thrust output, its structural feature is that the injection pipe (14) of air injection rotor (2) is tangentially not parallel with rotor, but an axial component is arranged, when jet rotary engine is worked, the air-flow of injection pipe (14) ejection promotes also can produce an end thrust the rotor rotation except a tangential thrust is arranged.
The core component of jet rotary engine is air injection rotor (2), will realize the compression of air, supercharging, fuel oil and air mixing burning and the combustion gas expansion ejection at a high speed of fuel oil in the inside of air injection rotor (2).This shows that the major function of jet rotary engine is finished in air injection rotor (2), so the parameter of air injection rotor (2) has determined the performance parameter of jet rotary engine fully.
Theory analysis shows that the most important structural parameter of jet rotary engine have three, the one, and firing chamber (13) rotational line speed V, the 2nd, firing chamber (13) products of combustion temperature T, the 3rd, injection pipe (14) critical section area S κ; Desirable hot merit transformation efficiency η of the performance parameter of jet rotary engine and desirable output power P can be expressed as the function of above three parameters, specifically are expressed as follows: η=V
2/ (W
0 2+ V
2), P=0.13S
kρ
0W
0 3η (1-η-T
0/ T)/(1-η)
5, wherein, W
0=750 meter per seconds are maximum jet velocities of air under the standard state; ρ
0=1.3 kilograms per cubic meter are the density of air under the standard state; T=293K is an air temperature under the standard state.
This shows that the rotational line speed of rotor firing chamber (13) is big more, the products of combustion temperature is high more, and the jet rotary engine performance is good more.And firing chamber (13) maximum structural strength that allows rotational line speed to be decided by rotor, the maximum temperature of products of combustion can not be higher than the heatproof upper limit of firing chamber (13), this just requires the air injection rotor (2) of jet rotary engine should adopt the strong material of height ratio, for example, Ti alloy with high performance, carbon fiber composite etc., and require firing chamber (13) and injection pipe (14) to answer high-temperature resistant material of inner lining, for example silicon carbide, silicon nitride, the contour performance stupalith of aluminium oxide.
Jet rotary engine is made of six parts, and each parts has different schemes again, and these schemes can be combined into multiple jet rotary engine scheme, has provided the exemplary of this combination in the following embodiments.
Description of drawings:
Figure one is the air injection rotor structural drawing of jet rotary engine;
Figure two is embodiment's one structural drawing;
Figure three is embodiment's two structural drawing;
Figure four is embodiment's three structural drawing;
Figure five is embodiment's four structural drawing;
Figure six is embodiment's five structural drawing;
Figure seven is embodiment's six structural drawing.
Embodiment one: single rotor axle output jet rotary engine
Structure: body (1), rotor chamber (9), air injection rotor (2), Fuel System (3), combustion gas system (4), starting system (5).Its structural feature is, rotor type is a liquid fuel type, and combustion gas system (4) has only rotor gas circuit (7) to constitute, and output type is that rotor shaft is directly exported.
Parameter: critical section area S
k=3 square centimeters, rated speed n=60000 rev/min, rotor radius R=13 centimetre, rated power p=100 kilowatt, throughput m=0.43 Kilograms Per Second, efficiency eta=41%, specified fuel oil speed G=6 Grams Per Second.
Embodiment two: the turbocharging type jet rotary engine
Structure: body (1), rotor turbine chamber (9), air injection rotor (2), Fuel System (3), starting system (5), compression impeller (33), turbine (34).Its structural feature is, rotor type is a liquid fuel type, combustion gas system (4) comprises preceding stage compressor (33) and back level combustion gas Conversion of energy turbine (34), compressor (33) is driven by turbine (34), power is by the rotating shaft output of air injection rotor (2), air-flow between air injection rotor (2) and the turbine (34) is coupled as the speed coupling, and turbine (34) is the turbine of tangential influent stream.
Parameter: critical section area S
k=3 square centimeters, rated speed n=60000 rev/min, rotor radius R=13 centimetre, rated power p=160 kilowatt, throughput m=0.58 Kilograms Per Second, efficiency eta=62%, specified fuel oil speed G=6.5 Grams Per Second.
Embodiment three: turbine output type jet rotary engine
Structure: body (1), rotor chamber (9), air injection rotor (2), Fuel System (3), starting system (5), turbine (34).Its structural feature is, rotor type is a liquid fuel type, and combustion gas system (4) comprises preceding stage compressor (33) and back level combustion gas Conversion of energy turbine (34), and compressor (33) is by turbine (34) driving, and power is exported by turbine (34).Only as the work of high-pressure gas generator, the air-flow between air injection rotor (2) and the turbine (34) is coupled as coupling pressure to air injection rotor (2).
Parameter: critical section area S
k=3 square centimeters, rated speed n=60000 rev/min, rotor radius R=13 centimetre, rated power p=120 kilowatt, throughput m=0.43 Kilograms Per Second, efficiency eta=50%, specified fuel oil speed G=6 Grams Per Second.
Embodiment four: the rocket jet propeller cavitation
Structure: air injection rotor (2) external form is a propeller cavitation, and fuel used is katergol, comprises liquid oxidizer and reducing agent.The jet rotary engine structure of this form is very simple, and does not need the starting arrangement can own quick starting, is suitable for the aircraft power as hop.
Embodiment five: the double rotor jet-propeller
Structure: lesser trochanter (2), greater trochanter (34), lesser trochanter chamber (9) are in the propeller boss of greater trochanter (34), and the high-pressure gas that lesser trochanter (2) produces directly enters the blast tube of greater trochanter (34), and tangentially spray from the nozzle of greater trochanter (34).Its structural feature is, have small one and large one two rotors, the profile of greater trochanter (34) is a propeller-like, and lesser trochanter (2) is packed in the propeller boss of greater trochanter (34), as the high-pressure gas generator, greater trochanter (34) utilizes the high-pressure gas work of lesser trochanter (2) generation during lesser trochanter (2) running.The jet rotary engine of this form can be used as helicopter screw propeller.
Parameter: lesser trochanter critical section area S
k=3 square centimeters, lesser trochanter rated speed n
1=60000 rev/mins, the lesser trochanter radius R
1=13 centimetres, greater trochanter rated speed n
2=600 rev/mins, the greater trochanter radius R
2=5 meters, rated power p=44 kilowatt, throughput m=0.50 Kilograms Per Second, efficiency eta=35%, specified fuel oil speed G=3 Grams Per Second.
Embodiment six: end thrust formula jet rotary engine
Structure: body (1), air injection rotor (2), Fuel System (3), starting system (5), rotor-injection pipe (14) are α with tangential angle.Its structural feature is, the injection pipe (14) of air injection rotor (2) is tangentially not parallel with rotor, but an axial component is arranged, when jet rotary engine is worked, the air-flow of injection pipe (14) ejection promotes also can produce an end thrust the rotor rotation except a tangential thrust is arranged.The jet rotary engine of this form can be used as the power of small aircraft.
Parameter: critical section area S
k=3cm
2, rated speed n=60000 rev/min, rotor radius R=13 centimetre, injection pipe and the tangential angle of rotor just be cut to 1/2, throughput m=0.52 Kilograms Per Second, specified fuel oil speed G=0.9 Grams Per Second, normal thrust F=195 newton.
Claims (2)
1. a jet rotary engine is characterized in that, it is made of body (1), air injection rotor (2), Fuel System (3), combustion gas system (4), starting system (5), power output device (6) six parts;
The profile of air injection rotor (2) and mass distribution be with respect to the strict symmetry of rotating shaft, and have enough big structural strength, rotor by rotating shaft, Bearing Installation on body (1); Be provided with two or more rotor gas circuit (7) that is distributed symmetrically each other and rotor oil circuit (8) at internal rotor; Every rotor gas circuit (7) is made of suction port (11), the centrifugal air pressure draw (12), firing chamber (13), injection pipe (14) four parts; Suction port (11) is near the rotor end-face axle center, the centrifugal air pressure draw (12) is communicated with suction port (11) and firing chamber (13), firing chamber (13) is in the rotor outside, the distance in axle center is arrived in firing chamber (13) greater than suction port (11) to the distance in axle center, the inlet of injection pipe (14) is in the firing chamber (13), outlet is at rotor side surface, and the centerline average of injection pipe (14) is parallel with the rotor tangent line, also can one little angle be arranged the sub-tangent line of transfer; The inwall of firing chamber (13) and injection pipe (14) is lined with heat insulation temperature-resistant material; Rotor oil circuit (8) is made of oil inlet hole (15), centrifugal fuel pressurization pipe (16), oil injecting nozzle (17) three parts; Oil inlet hole (15) is connected with fuel supply line in rotor axis and by rotary seal, and centrifugal fuel pressurization pipe (16) is communicated with oil inlet hole (15) and oil injecting nozzle (17), and the opening of oil injecting nozzle (17) is in the firing chamber (13); Above scheme is suitable for adopting the jet rotary engine of liquid fuel; According to fuel used difference, air injection rotor (2) also has other two kinds of schemes: a kind of is the gaseous fuel formula, its structural feature is not have rotor oil circuit (8), and gaseous fuel is elder generation and air mixing before entering rotor, enters rotor gas circuit (7) by suction port (11) again; Also having a kind of is the rocket fuel formula, is characterized in carrying liquid fuel and liquid oxidizer, does not need air to get final product work, thereby air injection rotor (2) does not have the suction port (11) and the centrifugal air pressure draw (12); The service performance of rocket fuel formula jet rotary engine is that the working pressure transfer rotor speed of firing chamber (13) is irrelevant, but motor need not add the starting arrangement self-drive;
Fuel System (3) is made of fuel tank (21), delivery rate controller (22), fuel supply line (23), several parts of rotor oil circuit (8), and delivery rate controller (22) can provide suitable delivery rate according to instruction of being sent and jet rotary engine running operating mode;
The most complete composition proposal of combustion gas system (4) is made of air-strainer (31), suction tude (32), prime air compression plant (33), rotor gas circuit (7), back level combustion gas energy conversion device (34), outlet pipe (35); Wherein having only rotor gas circuit (7) is combustion gas system (4) indispensable core; The simplest combustion gas is that (4) organization plan only has rotor gas circuit (7) to constitute; Another scheme is that combustion gas system (4) is provided with prime air compression plant (33), but level combustion gas energy conversion device (34) not; The structure of prime air compression plant (33) is a centrifugal compressor or axial flow compressor, and it can be driven by air injection rotor (2), also can be driven by back level combustion gas energy conversion device (34); Back level combustion gas energy conversion device (34) can be a turbine mechanism, also can be a piston mechanism, its function is to be the combustion gas Conversion of energy of high-voltage high-speed mechanical work, flow parameter coupled modes between back level combustion gas energy conversion device (34) and the air injection rotor (2) can employing speed be coupled, the gas pressure that is air injection rotor (2) ejection equals barometric pressure substantially, the combustion gas energy mainly exists with the kinetic energy form, and the effect of back level energy conversion device (34) is that the kinetic energy of combustion gas is converted into the rotation merit; Also can adopt coupling pressure, i.e. the gas velocity of rotor (2) ejection is zero substantially, and pressure is greater than barometric pressure, and the effect of back level combustion gas energy conversion device (34) is that the pressure potential of combustion gas is converted into the rotation merit;
Starting system (5) is made of starter motor (41), starting circuit (42), igniter (43); The effect of starter motor (41) is to drive air injection rotor (2) to rotate when jet rotary engine starts, and makes air injection rotor (2) obtain the necessary initial velocity of starting; Igniter (43) is contained in the firing chamber (13), and the acting in conjunction of starting circuit (42) and igniter (43) is when jet rotary engine starts, and carries out initial ignition for firing chamber (13); When running well after the jet rotary engine starting, starting system (5) quits work;
The scheme of power output device (6) has four kinds: the one, directly to export by the rotating shaft of air injection rotor (2), i.e. and rotating shaft by air injection rotor (2) directly or by gear transmission drives load, is the prevailing way of output; The 2nd, by back level combustion gas energy conversion device (34) output, the characteristics of this scheme are that air injection rotor (2) is only as gasifier section work, the high-pressure gas that it produced is converted into mechanical energy in back level combustion gas energy conversion device (34), and drives the load work done; The 3rd, export in the mode of propeller cavitation, the structural feature of this scheme is that itself just to make profile be propeller-like to air injection rotor (2), firing chamber (13) and injection pipe (14) just are located at the outer end of blade, and during jet rotary engine work, injection pipe (14) directly promotes propeller cavitation and rotates; The 4th, end thrust output, its structural feature is that the injection pipe (14) of air injection rotor (2) is tangentially not parallel with rotor, but an axial component is arranged, when jet rotary engine is worked, the air-flow of injection pipe (14) ejection promotes also can produce an end thrust the rotor rotation except a tangential thrust is arranged;
Each parts of jet rotary engine can have different schemes, these schemes make up mutually and can provide multiple multi-form jet rotary engine, and the basic demand of every kind of combination is can cooperatively interact between each parts also to be mounted to the integral body of a harmony unanimity;
2. a kind of jet rotary engine that provides according to claim 1 is characterized in that, the fundamental relation between the parameter is η=V
2/ (W
0 2+ V
2), P=0.13S
kρ
0W
0 3η (1-η-T
0/ T)/(1-η)
5, wherein, V is firing chamber (a 13) rotational line speed; T is the products of combustion temperature; S
κBe injection pipe (14) critical section area; η is desirable hot merit transformation efficiency; P is the motor ideal power; ρ
0Be suction port (11) air density; T
0Be suction port (11) air temperature; W
0Be the maximum jet velocity of suction port (11) air.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00132754 CN1234966C (en) | 2000-11-17 | 2000-11-17 | Jet rotary engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00132754 CN1234966C (en) | 2000-11-17 | 2000-11-17 | Jet rotary engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1354322A true CN1354322A (en) | 2002-06-19 |
| CN1234966C CN1234966C (en) | 2006-01-04 |
Family
ID=4595376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 00132754 Expired - Fee Related CN1234966C (en) | 2000-11-17 | 2000-11-17 | Jet rotary engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1234966C (en) |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008014689A1 (en) * | 2006-07-27 | 2008-02-07 | Yuexiang Bao | An internal combustion steam rotor engine |
| CN101501319B (en) * | 2006-06-09 | 2011-03-09 | 贝尔直升机泰克斯特龙公司 | Engine exhaust system with directional nozzle |
| CN103016205A (en) * | 2012-09-09 | 2013-04-03 | 陈久斌 | Flywheel engine |
| CN103452669A (en) * | 2013-09-10 | 2013-12-18 | 程永华 | Fuel gas autorotation type engine |
| CN103573471A (en) * | 2012-10-08 | 2014-02-12 | 摩尔动力(北京)技术股份有限公司 | Pre-supercharging rotating stamping engine |
| CN103590920A (en) * | 2012-10-23 | 2014-02-19 | 摩尔动力(北京)技术股份有限公司 | Propeller |
| CN103590919A (en) * | 2012-10-22 | 2014-02-19 | 摩尔动力(北京)技术股份有限公司 | High-pressure jet-propelled rotary engine |
| CN103590905A (en) * | 2013-05-19 | 2014-02-19 | 摩尔动力(北京)技术股份有限公司 | Method for realizing efficient heat-work conversion and engine applying same |
| CN103644042A (en) * | 2012-12-25 | 2014-03-19 | 摩尔动力(北京)技术股份有限公司 | Jet rotor engine |
| CN103850795A (en) * | 2013-03-11 | 2014-06-11 | 摩尔动力(北京)技术股份有限公司 | Multi-turntable engine |
| CN103867298A (en) * | 2013-02-18 | 2014-06-18 | 摩尔动力(北京)技术股份有限公司 | Remote-control external combustion rotor engine |
| CN103867301A (en) * | 2013-02-18 | 2014-06-18 | 摩尔动力(北京)技术股份有限公司 | Remote-control internal combustion rotor engine |
| CN103867491A (en) * | 2013-02-18 | 2014-06-18 | 摩尔动力(北京)技术股份有限公司 | Rotating body liquid remote supply device for engine |
| CN103899418A (en) * | 2013-02-18 | 2014-07-02 | 摩尔动力(北京)技术股份有限公司 | Remotely-transferred rotor engine |
| CN103993979A (en) * | 2013-05-11 | 2014-08-20 | 摩尔动力(北京)技术股份有限公司 | Phase-change engine |
| CN104153913A (en) * | 2014-08-08 | 2014-11-19 | 罗雪琴 | Disc jet engine |
| CN107618654A (en) * | 2017-08-03 | 2018-01-23 | 南京航空航天大学 | Aircraft manufacturing technology system and its control method, control nozzle |
| CN107702487A (en) * | 2017-11-02 | 2018-02-16 | 浙江燕思志网络科技有限公司 | A kind of Chinese medicine Rapid Cleaning drying unit |
| CN107884533A (en) * | 2017-11-08 | 2018-04-06 | 苏州大学 | A kind of intelligent wireless water quality monitoring equipment and monitoring system |
| CN109139292A (en) * | 2018-09-12 | 2019-01-04 | 安徽工业大学 | A kind of rotary jet rotor |
| CN112081684A (en) * | 2019-06-12 | 2020-12-15 | 程浩鹏 | Jet fan engine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101550873B (en) * | 2009-04-29 | 2011-05-25 | 黄巴图 | A kind of internal combustion engine using biofuel |
-
2000
- 2000-11-17 CN CN 00132754 patent/CN1234966C/en not_active Expired - Fee Related
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101501319B (en) * | 2006-06-09 | 2011-03-09 | 贝尔直升机泰克斯特龙公司 | Engine exhaust system with directional nozzle |
| WO2008014689A1 (en) * | 2006-07-27 | 2008-02-07 | Yuexiang Bao | An internal combustion steam rotor engine |
| CN103016205A (en) * | 2012-09-09 | 2013-04-03 | 陈久斌 | Flywheel engine |
| CN103573471A (en) * | 2012-10-08 | 2014-02-12 | 摩尔动力(北京)技术股份有限公司 | Pre-supercharging rotating stamping engine |
| CN103590919A (en) * | 2012-10-22 | 2014-02-19 | 摩尔动力(北京)技术股份有限公司 | High-pressure jet-propelled rotary engine |
| CN103590920A (en) * | 2012-10-23 | 2014-02-19 | 摩尔动力(北京)技术股份有限公司 | Propeller |
| CN103644042A (en) * | 2012-12-25 | 2014-03-19 | 摩尔动力(北京)技术股份有限公司 | Jet rotor engine |
| CN103867298A (en) * | 2013-02-18 | 2014-06-18 | 摩尔动力(北京)技术股份有限公司 | Remote-control external combustion rotor engine |
| CN103899418A (en) * | 2013-02-18 | 2014-07-02 | 摩尔动力(北京)技术股份有限公司 | Remotely-transferred rotor engine |
| CN103867301A (en) * | 2013-02-18 | 2014-06-18 | 摩尔动力(北京)技术股份有限公司 | Remote-control internal combustion rotor engine |
| CN103867491A (en) * | 2013-02-18 | 2014-06-18 | 摩尔动力(北京)技术股份有限公司 | Rotating body liquid remote supply device for engine |
| CN103850795A (en) * | 2013-03-11 | 2014-06-11 | 摩尔动力(北京)技术股份有限公司 | Multi-turntable engine |
| CN103850795B (en) * | 2013-03-11 | 2016-04-27 | 摩尔动力(北京)技术股份有限公司 | Many rotating disks motor |
| CN103993979A (en) * | 2013-05-11 | 2014-08-20 | 摩尔动力(北京)技术股份有限公司 | Phase-change engine |
| CN103590905A (en) * | 2013-05-19 | 2014-02-19 | 摩尔动力(北京)技术股份有限公司 | Method for realizing efficient heat-work conversion and engine applying same |
| CN103452669A (en) * | 2013-09-10 | 2013-12-18 | 程永华 | Fuel gas autorotation type engine |
| CN104153913A (en) * | 2014-08-08 | 2014-11-19 | 罗雪琴 | Disc jet engine |
| CN107618654A (en) * | 2017-08-03 | 2018-01-23 | 南京航空航天大学 | Aircraft manufacturing technology system and its control method, control nozzle |
| CN107702487A (en) * | 2017-11-02 | 2018-02-16 | 浙江燕思志网络科技有限公司 | A kind of Chinese medicine Rapid Cleaning drying unit |
| CN107884533A (en) * | 2017-11-08 | 2018-04-06 | 苏州大学 | A kind of intelligent wireless water quality monitoring equipment and monitoring system |
| CN109139292A (en) * | 2018-09-12 | 2019-01-04 | 安徽工业大学 | A kind of rotary jet rotor |
| CN112081684A (en) * | 2019-06-12 | 2020-12-15 | 程浩鹏 | Jet fan engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1234966C (en) | 2006-01-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1234966C (en) | Jet rotary engine | |
| CN101338702B (en) | Pulse knock rotor spindle engine | |
| CN1092289C (en) | Ramjet engine for power generation | |
| CN1319718A (en) | Method for generating power | |
| EP1088158A1 (en) | Ramjet engine for power generation | |
| US4873825A (en) | Positive displacement engine compounded with a gas turbine engine | |
| US6418707B1 (en) | General advanced power system | |
| CN2695659Y (en) | Composite ramjet and fanjet engine | |
| CN2620100Y (en) | Combined fanjet | |
| CN1234962C (en) | Centrifugal engine | |
| WO2000019082A9 (en) | Ramjet engine with axial air supply fan | |
| CN216240936U (en) | Engine | |
| CN2038551U (en) | Double working-substance steam-gas turbine | |
| CN1210494C (en) | Reaction rotor engine | |
| CN218760158U (en) | Engine with variable bypass ratio realized by motor with rotating booster stage | |
| CN112459902B (en) | Mechanical transmission structure, hybrid power supercharging device and engine exhaust system | |
| CN212479415U (en) | Multi-stage inter-cooling gas turbine power generation system combining supercharger and micro-gas turbine | |
| CN105569846A (en) | Rotary jet internal combustion engine capable of achieving combustion twice | |
| RU2815564C1 (en) | Aircraft power plant | |
| CN219840723U (en) | Distributed propulsion variable cycle engine | |
| CN2515432Y (en) | Contrarotating gear jet engine | |
| CN85101085A (en) | Piston-type hydraulic conveying internal combustion engine with no crankshafts | |
| CN203640864U (en) | Pressure boosting device used for turbine engine | |
| RU2334892C1 (en) | Turboprop gas turbine engine | |
| CN114180029A (en) | Propeller assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |